A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

A gas turbine engine comprises a fan; an engine core comprising a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox; an Engine Section Stator (ESS) comprising a plurality of ESS vanes with an external surface washed by the core airflow; an ESS heating system adapted to heat the ESS vanes, and a temperature sensor adapted to detect the temperature of the external surface of the ESS vanes and send a signal to the ESS heating system when said temperature is below a reference temperature. Upon detection and/or inference of ice crystal conditions and receiving from the temperature sensor the signal that the temperature is below the reference temperature, the ESS heating system is activated to heat at least a portion of the external surface of the ESS vanes and promote melting and adhering of ice crystals thereto.

A gas turbine engine comprises a fan; an engine core comprising a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox; an Engine Section Stator (ESS) comprising a plurality of ESS vanes with an external surface washed by the core airflow; an ESS heating system adapted to heat the ESS vanes, and a temperature sensor adapted to detect the temperature of the external surface of the ESS vanes and send a signal to the ESS heating system when said temperature is below a reference temperature. Upon detection and/or inference of ice crystal conditions and receiving from the temperature sensor the signal that the temperature is below the reference temperature, the ESS heating system is activated to heat at least a portion of the external surface of the ESS vanes and promote melting and adhering of ice crystals thereto.

A fluid viscosity system for use in a gas turbine engine includes an induction assembly coupled to a fluid line within the gas turbine engine. The induction assembly includes an electromagnet. The induction assembly further includes an electronic oscillator electronically coupled to the electromagnet. The electronic oscillator is configured to generate an alternating current (AC) that is transmitted to the electromagnet at a predetermined frequency and magnitude such that a viscosity of a fluid channeled through the fluid line is reduced at least partially due to induction heating.

A fluid viscosity system for use in a gas turbine engine includes an induction assembly coupled to a fluid line within the gas turbine engine. The induction assembly includes an electromagnet. The induction assembly further includes an electronic oscillator electronically coupled to the electromagnet. The electronic oscillator is configured to generate an alternating current (AC) that is transmitted to the electromagnet at a predetermined frequency and magnitude such that a viscosity of a fluid channeled through the fluid line is reduced at least partially due to induction heating.

A system includes a compressor having a compressor inlet, a turbine having a plurality of stages disposed within a turbine casing, and a turbine extraction gas (TEG) heating system. The turbine is configured to drive the compressor via expansion of combustion products through the plurality of stages. The TEG heating system includes a turbine gas extraction system coupled to the turbine casing and to the compressor inlet. The turbine gas extraction system is configured to receive a portion of the combustion products as a turbine extraction gas (TEG) from the turbine. The TEG is received through the turbine casing, the TEG heating system is configured to supply a heated flow to the compressor inlet, and the heated flow includes the TEG.

A turbocharger includes a turbine housing, a compressor housing, and a bearing housing. Each of the housings includes a passage for cooling inside. The turbocharger further includes a switching valve and a controller that switches a valve position of the switching valve. The switching valve is adapted to switch the circulation state of coolant in each passage such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing or such that the coolant is supplied from another passage to the passage of the bearing housing. The controller switches the valve position of the switching valve such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing until a predetermined amount of time passes after starting of the engine.

A turbocharger includes a turbine housing, a compressor housing, and a bearing housing. Each of the housings includes a passage for cooling inside. The turbocharger further includes a switching valve and a controller that switches a valve position of the switching valve. The switching valve is adapted to switch the circulation state of coolant in each passage such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing or such that the coolant is supplied from another passage to the passage of the bearing housing. The controller switches the valve position of the switching valve such that the coolant is supplied from the passage of the turbine housing to the passage of the bearing housing until a predetermined amount of time passes after starting of the engine.